Fan Containment case for gas turbine engines

Abstract

A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan containment case assembly that has an outer case extending about an axis, and a thermally conforming liner assembly radially inward of the outer case. The liner assembly has a shell, a wrap radially outward of the shell, and a ballistic liner between the outer case and the wrap. The wrap has a first fiber construction, and the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness.

What is claimed is: 
     
       1. A fan section for a gas turbine engine comprising:
 a fan containment case assembly including:
 an outer case extending about an axis; 
 a thermally conforming liner assembly radially inward of the outer case, the liner assembly including a shell; 
 a wrap radially outward of the shell; and 
 a ballistic liner between the outer case and the wrap; 
 wherein the wrap has a first fiber construction, the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness, the wrap directly contacts an outer diameter of the shell, and the first fiber construction of the wrap is made of substantially non-impregnated fibers. 
 
 
     
     
       2. The fan section as recited in  claim 1 , wherein the second fiber construction of the ballistic liner is made of resin impregnated fibers. 
     
     
       3. The fan section as recited in  claim 2 , wherein the fibers of the first fiber construction are aramid fibers. 
     
     
       4. The fan section as recited in  claim 3 , wherein the outer case is made of a composite material. 
     
     
       5. The fan section as recited in  claim 1 , comprising a plurality of fan blades rotatable about the axis within a fan blade region of the fan containment case assembly. 
     
     
       6. The fan section as recited in  claim 5 , wherein each of the ballistic liner and the wrap circumferentially surrounds the plurality of fan blades. 
     
     
       7. The fan section as recited in  claim 5 , wherein:
 the shell includes a first section, a second section located aft of the first section, and a third section located aft of the second section; and 
 the thermally conforming liner assembly includes a forward acoustic liner radially inward of the first section of the shell, an abradable rub layer defining a clearance gap with the plurality of fan blades, and a honeycomb core between the second section of the shell and the abradable rub layer. 
 
     
     
       8. The fan section as recited in  claim 6 , comprising a plurality of ribs circumferentially distributed about the outer diameter of the shell, and a plurality of torque blocks mechanically attached to the outer case, wherein at least one torque block of the plurality of torque blocks being positioned between at least one pair of the plurality of ribs to oppose rotation of the shell relative to the outer case. 
     
     
       9. A gas turbine engine comprising:
 a fan including a plurality of fan blades rotatable about an engine longitudinal axis; 
 a compressor section; 
 a turbine section driving the fan; and 
 a fan containment case assembly comprising:
 an outer case extending about the engine longitudinal axis; 
 a thermally conforming liner assembly radially inward of the outer case, the liner assembly including a shell; 
 a wrap between the outer case and the shell, at least partially surrounding the plurality of fan blades, and made of substantially non-impregnated fibers; and 
 a ballistic liner between the outer case and the wrap. 
 
 
     
     
       10. The gas turbine engine as recited in  claim 9 , wherein the ballistic liner comprises a metal material. 
     
     
       11. The gas turbine engine as recited in  claim 9 , wherein the ballistic liner is made of resin impregnated fibers, the wrap is bonded to an outer diameter of the shell, and the ballistic liner is bonded to the outer case. 
     
     
       12. A gas turbine engine comprising:
 a fan including a plurality of fan blades rotatable about an engine longitudinal axis; 
 a compressor section; 
 a turbine section driving the fan; and 
 a fan containment case assembly comprising:
 an outer case extending about the engine longitudinal axis; 
 a thermally conforming liner assembly radially inward of the outer case, the liner assembly including a shell; 
 a wrap between the outer case and the shell, at least partially surrounding the plurality of fan blades, and made of substantially non-impregnated fibers; and 
 wherein the outer case is made of a composite material. 
 
 
     
     
       13. A method of assembling a fan containment case comprising:
 attaching a ballistic liner to an inner diameter of an outer case; 
 preparing a thermally conforming liner assembly, including attaching a wrap to an outer diameter of a shell, the wrap made of substantially non-impregnated fibers; and 
 positioning the thermally conforming liner assembly radially inward of the ballistic liner. 
 
     
     
       14. The method as recited in  claim 13 , comprising positioning the thermally conforming liner assembly to at least partially surround a plurality of fan blades. 
     
     
       15. The method as recited in  claim 14 , wherein the step of preparing includes attaching an acoustic liner to an inner diameter of the shell, attaching a honeycomb core to an inner diameter of the shell, and attaching an abradable rub layer to an inner diameter of the honeycomb core, the abradable rub layer defining a gas flowpath surface adjacent to a plurality of fan blades. 
     
     
       16. The method as recited in  claim 13 , wherein the ballistic liner is made of resin impregnated fibers. 
     
     
       17. The method as recited in  claim 13 , wherein the step of preparing includes attaching a plurality of ribs to the shell, and the step of positioning includes axially aligning the plurality of ribs between a plurality of torque blocks of the outer case to oppose rotation of the thermally conforming liner assembly relative to the outer case. 
     
     
       18. The fan section as recited in  claim 1 , wherein the outer case is made of a composite material. 
     
     
       19. The gas turbine engine as recited in  claim 9 , wherein the outer case is made of a composite material. 
     
     
       20. The method as recited in  claim 13 , wherein the outer case is made of a composite material.